Propeller



J. BARTON July 5, 1927.

PROPELLER Filed Feb. 1 0, 1926 Patented July 5, 1927.

1,534,393 PATENT OFFICE.v

JOHN BARTON, OF MATADOR, TEXAS.

PROPELLER.

Application filed February 10, 1926.

The present invention relates to improvements in propellers, and is more particularly adapted to a propeller for use upon aeroplanes.

One o the important objects of thepresent invention is to provide a propeller wherein means is provided for adjusting the incidence of the blades whereby a much greater thrustarea is obtained, and further enabling the plane to attain high speed with a relatively low E. P. M.of the motor.

A further object is to provide an aeroplane propeller of the above mentioned character wherein the blades are further adapted for adjustment with respect to each other so that the plane may ascend at'a-greater angle than is possible by the use of any other propeller, and by such adjustments the plane may ascend at a greater angle and the propeller still exert a pulling force and not merely slip through the air.

A further object is to provide an aeroplane propeller which may be readily and easily assembled, the same being further simple in construction, inexpensive, strong and durable and further well adapted to the purpose for which it is designed.

In the accompanying drawing forming a part of this application and in which like numerals designate like parts throughout the same:

Figure l is a front elevation of the propeller embodying my invention.

Figure 2 is a side elevation thereof.

Figure 3 is a fragmentary sectional view through the hub showing the manner in which the blades are secured thereon, and

Figure 4 is an elevational View of one of the blades.

Fig. 5 is a sectional view taken approximately on line 5-5 of Fig. 2 showing more clearly the construction of the stream line design of the stay'bolt.

In the drawing wherein for the purpose of illustration is shown the preferred em bodiment of my invention, the numeral 1 designates generally my improved propeller, the same being of substantially circular form, and further comprising the complementary semi-circular blades 2 and 3. Each blade is formed of any suitable thin metallic material, such as aluminum or the like, although it is to be understood that I do not wish to limit myself to the particular kind of material which may be used in constructing the propeller. Each of the blades is pro- Serial No. 87,347.

vided with an enlarged opening 4 in the center thereof and adjacent the straight edge and the purpose of this construction is to provide a means whereby the blade may be placed on the hub 5 which is adapted to be secured on the outer end of the crank shaft of the aeroplane engine (not shown) in the manner well known in the art. An annular flange 6 is formed on the hub 5 adjacent the inner end thereof and cooperating therewith is the ring 7 and the collar 8, the latter two elements being slidable on the outer end of the hub. The intermediate portions of the blades are adapted to be disposed on thehub between the flange 6 and the ring 7 and suitable bolts 9 extend through registering open ings provided therefor in the flange, ring, collar, as well as through the openings 10 formed in each of the blades around its open ing 41 so that the parts are securely held on the hub against accidental displacement therefrom.

Each blade is provided with an inwardly extending slot 11 adjacent the opening 4,

and provides a means for acommodating the straight edge portions of the respective blades so that the blades 2 and 3 may be disposed in intersecting or angular relation with respect to one another. tions of each of the blades are further bent or curved in the manner as more clearly illustrated in Figure 2, whereby the adjacent ends of the blades are spaced from each other. 7

Suitable rivets or other fastening means indicated at 12 provides a means for securing the abutting central portions of the blades adjacent the hub 5 as is clearly shown in Figure 3, to further insure the securing of the blades in proper relation with respect to each other.

For the purpose of adjustably securing the adjacent straight edge portions of the blades at the ends thereof, I provide the stay bolts 13, the same being preferably of stream line design, suitable lock nuts 14 are threaded on each end of each stay bolt, and the same are disposed on opposite sides of each of the blades in the manner as more clearly shown in Figure 2. It is obvious that by loosening the nuts 14:, the ends of the blades may be moved along the bolts 13, so that the incidence or pitch of the blades may be adjusted to the desired degree so as to enable the aeroplane to attain a relatively high speed and a strong pull with a relatively The end porlow E. P. lvLolf the motor or engine of the aeroplane. Furthermore, a much greater thrust area is obtained, Also, a propeller construction of the above character will make it possible for the aeroplane to ascend vertically at substantially right angles to the ground.

The simplicity in which my propeller is constructed enables the same to be readily and easily assembled, and will further be strong and durable, and at all times positive and eti'icient in carrying out the nurposes for which it is designed.

While I have shown the preferred embodiment of m invention, it is to be understood that minor changes in the size, shape and ar angement of parts may be resorted to without departing from the spirit of the invention and the scope of the appended claims.

Having thus described the invention, What I claim as new and desire to secure by Letters Patent is 2- 1. In a propeller comprising a hub, a flange -formed thereon adjacent the inner end thereof, a pair of substantially semicircular blades, each blade being provided with an opening to permit the blades to be disposed on the hub, one of the blades being provided with a slot which extends inwardly of the straight edge thereof, to accommodate the adjacent straight edge portion of the other blade whereby the blades are disposed in intersecting relation, a ring slidable on the outer end portion of the hub and adapted for engagement with the intermediate portions oil said blades, bolts extending through the flange and the ring as well as through the central portions of the intersecting blades, the central portions of the blades being secured in abutting relation, the outer ends or the blades being curved in opposite directions.

2. jrpropeller comprising a hub, a pair of semi-circular blades mounted thereon, said blades being disposed in intersecting relation with respect to each other, and means for adjusting t1 e pitch between the blades, said lastmentioned means comprising stay bolts of stream line design having their respective ends threaded and extending through the free ends or the adjacent blades, and lock nuts threaded on each end of the bolts and engaging the respective faces of each of the blades. 7

in. testimony whereof I afliX my signature.

, JOHN BARTON. 

